CN101081638B - Unmanned aerial plane launching system and method - Google Patents
Unmanned aerial plane launching system and method Download PDFInfo
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- CN101081638B CN101081638B CN2006100357635A CN200610035763A CN101081638B CN 101081638 B CN101081638 B CN 101081638B CN 2006100357635 A CN2006100357635 A CN 2006100357635A CN 200610035763 A CN200610035763 A CN 200610035763A CN 101081638 B CN101081638 B CN 101081638B
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- guide rail
- unmanned aerial
- support body
- coaster
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Abstract
The present invention relates to drone, and is especially system and method of launching drone. The drone launching system includes one guide rail system, one ejecting system, one braking system, one control system and one power source. The ejecting system and the braking system are set on the guide rail system, the control system controls the ejecting system and the braking system, the ejecting system includes one power system with one rubber band bundle serving as elastomer to store energy. During being launched, the drone is powered by the elastomer to accelerate in the guide rail. The present invention has low drone launching cost.
Description
Technical field
The present invention relates to a kind of Unmanned Aircraft Systems (UAS), particularly a kind of unmanned aerial plane launching system and method.
Background technology
Unmanned plane (UAV) is the abbreviation of " robot airplane ", mainly relies on radio telecommand or realizes Autonomous Control flight by modes such as autopilots.It is one of current advanced technological arms, extensively applies to many warlike operations such as battle reconnaissance, electronic countermeasure, air attack, is described as " prying eyes " and " trump card " of modern battlefield.At present, the UAV emission coefficient of China mainly adopts hydraulic pressure, pneumatic, these several launch modes of rocket assist.These several launch modes exist complex structure, make the use cost height, the problem of maintenance difficulty.The safety measure of using as the transportation of booster rocket, storage requires high, for its use brings very big inconvenience.And the rocket assist emission coefficient, because of rocket can not repeated usage, each launch cost only one in rocket just needs thousands of units.The hydraulic pressure emission coefficient cause 1,000,000 yuan of Ben Gaoda.
Summary of the invention
The objective of the invention is to, a kind of simple in structure, cheap, unmanned aerial plane launching system that can be reusable, safe and reliable is provided.
Another object of the present invention is, a kind of unmanned plane method for transmitting is provided.
The objective of the invention is to realize by the following technical solutions:
A kind of unmanned aerial plane launching system comprises guide track system, ejection system, brake system, control system and propulsion source; Described ejection system and brake system are arranged on the described guide track system; Described control system is controlled described ejection system and brake system; Described ejection system comprises that one is the power system of power with the elastic body stored energy.
Described guide track system comprises guide rail, support body, and the upper surface that described guide rail is positioned at support body extends along described support body length direction.
Described guide rail and support body are divided into two sections at least, link to each other two sections can be folding relatively.
Described guide rail and support body are divided into two sections at least, and the two sections correspondences that link to each other are nested.
Described elastic body is the elastic bundle.
A kind of unmanned plane launching technique, described unmanned plane emission is a power with the elastic body stored energy.Described elastic body is the elastic bundle.
The present invention utilizes the power of elastic body as the unmanned plane emission, utilize guide rail to quicken to unmanned plane, make unmanned plane reach the scheme of leaving guide rail behind certain rate of onset, the most basic low price of utilizing, the energy storage characteristic of the elastic body that can be repeatedly used (elastic), apply in the moment output of energy of concrete UAV emission coefficient, reach the reduction use cost; Native system is simple in structure simultaneously, is convenient to grasp, and is easy to use, reaches safe, the easy and failure-free requirement when using.
Description of drawings:
Fig. 1 is an integral structure scheme drawing of the present invention;
Fig. 2 is the shaft side figure of structural representation shown in Figure 1;
Fig. 3 is the scheme drawing of ejection system of the present invention and brake system;
The specific embodiment
Embodiment one
As shown in Figure 1, 2, 3, a kind of unmanned aerial plane launching system comprises guide track system, ejection system, brake system, control system and propulsion source; Described ejection system and brake system are arranged on the described guide track system; Described control system is controlled described ejection system and brake system, and propulsion source provides the energy for total system.
Described guide track system comprises guide rail 1, support body 2, and described guide rail 1 is the upper surface that is positioned at support body 2, along two of described support body 2 length directions extension parallel threads; Described guide rail 1 and support body 2 can be that integral body is design, also can be to be divided into two sections at least, link to each other two sections can be folding relatively; In order to reduce manufacture difficulty and to be convenient to transportation, adopt three sections guide rails 11,12,13 in the present embodiment, support body 21,22,23 folding forms are connected with lock(ing) bolt by hinge between each section, but can manually fold also auto-folder.For the ease of moving of unmanned aerial plane launching system, can design a towing carriage 3 that has a wheel, it is fastening by connecting element that described support body 2 is placed on the described towing carriage 3 back.Towing carriage 3 preferably is designed to regulate height, places the needs of angle to cooperate guide rail.
Described ejection system comprises power system and coaster 4, and described coaster 4 can move along described guide rail 1 under the effect of described power system, and unmanned plane is placed on the described coaster 4; Described power system comprises winch truck 5, a cable wire 6 and a stretchable elastic body 7 under described drive power source, adopts the elastic bundle in the present embodiment; Described cable wire 6 one terminations are gone into described winch truck 5, one ends and are linked to each other with described coaster 4, and described cable wire 6 links to each other with the free end of described elastic body 7 versatilely, and the other end of described elastic body 7 is fixed on the described support body 2; When described coaster 4 was fixed on initial position, described elastic body 7 was stretched under the effect of described winch truck 5 and cable wire 6, accumulates elastic energy.
Described brake system is after being used for reducing unmanned plane and obtaining rate of onset and leave described coaster, continue with higher speed to the terminal motion of guide rail and smash described guide track system in order to prevent described coaster, even described coaster 4 flies out.In the present embodiment, the shared cover power system of described brake system and described ejection system; After unmanned plane acquisition rate of onset leaves described coaster, along with the change of cable wire direction, coaster will be subjected to pulling force backward, and speed reduces can not produce harmful effect to guide track system until stopping gradually.
Described propulsion source is electrical motor, electrical generator or storage battery.
The working process of described unmanned aerial plane launching system is as follows: earlier coaster is locked in the initial point of emission, unmanned plane is locked on the carriage again, insert safety pin.Propulsion source provides the energy for power system, makes elastic body reach certain energy storage.Remove safety pin then, emission coefficient is in battery, and after launch intruction was assigned, the lockout mechanism of coaster was opened, and discharges coaster.Coaster is under the effect of elastomer contracts power, and during the position quicken to arrive set for unmanned plane on the guide rail of launcher by carriage, the body blocking device on the carriage is opened unmanned plane and gone up to the air from frame.Simultaneously, coaster enters the braking job procedure.Under the effect of brake system, coaster is under the effect of the negative acceleration that closed-center system provides, and pulsation-free obtains braking rapidly.
Embodiment two
The difference of the present embodiment and first embodiment is that described elastic body is large-scale extension spring bundle.
Embodiment three
The difference of the present embodiment and first embodiment is that guide rail 1 in the described guide track system and support body 2 are also formed by three sections, and only in the present embodiment, the described guide rail 1 two sections correspondences that link to each other with support body 2 are nested, are similar to a sleeve.
Embodiment four
The difference of the present embodiment and first embodiment is that described ejection system is in the not shared power system of described brake system.But the elastic body that independent employing can stretch comes to described coaster 4 resistances.Certainly, must be behind frame to the opportunity of coaster 4 resistances at unmanned plane.
Can know that from above-mentioned specific embodiment this system has the following advantages than other several emission coefficients: (1). low cost.Use and low cost of manufacture are one of the most outstanding advantages of this system, and what China UAV emission coefficient use at present was maximum is rocket assist.This rocket assist emission coefficient, because of rocket can not repeated usage, each launch cost only one in rocket just needs several thousand yuan.The manufacturing cost of hydraulic pressure emission coefficient is up to 1,000,000 yuan.
(2). simple in structure, be convenient to grasp, easy to use.Hydraulic pressure, emission coefficient physical structure complexity such as pneumatic have brought inconvenience for the maintenance of total system, need to cultivate the patent personnel it is safeguarded, have also increased use cost virtually.The transportation of booster rocket, storage and use all have high safety specifications, bring great inconvenience to use.
(3). system is reliable, safety.Reliability, safety are very important for the UAV emission coefficient.Complicated structure design is added and is safeguarded that improper meeting reduces the reliability of system greatly, and booster rocket in use has carelessness just the problem of personal safety to be arranged slightly.
In sum, this UAV emission coefficient has been mended a technological gap of domestic UAV emission coefficient.
The present invention also has other distortion such as elastomeric selection; The form of guide rail and support body can be made corresponding variation.If those skilled in the art does not need performing creative labour to make corresponding variation by inspiration of the present invention, all should fall into the protection domain of claim of the present invention.
Claims (5)
1. a unmanned aerial plane launching system comprises guide track system, ejection system, brake system, control system and propulsion source; Described ejection system and brake system are arranged on the described guide track system; Described control system is controlled described ejection system and brake system; Described ejection system comprises that one is the power system and a coaster of power with the elastic body stored energy, and described coaster moves along described guide track system under the effect of described power system; Described power system comprises winch truck, a cable wire and a stretchable elastic body under described drive power source; It is characterized in that described cable wire one termination is gone into described winch truck, an end links to each other with described coaster, and described cable wire links to each other with described elastomeric free end versatilely, and the described elastomeric other end is fixed on the described guide track system.
2. unmanned aerial plane launching system according to claim 1 is characterized in that described guide track system comprises guide rail, support body, and the upper surface that described guide rail is positioned at support body extends along described support body length direction.
3. unmanned aerial plane launching system according to claim 2 is characterized in that, described guide rail and support body are divided into two sections at least, link to each other two sections can be folding relatively.
4. unmanned aerial plane launching system according to claim 2 is characterized in that, described guide rail and support body are divided into two sections at least, and the two sections correspondences that link to each other are nested.
5. unmanned aerial plane launching system according to claim 1 and 2 is characterized in that, described elastic body is the elastic bundle.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2006100357635A CN101081638B (en) | 2006-06-02 | 2006-06-02 | Unmanned aerial plane launching system and method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2006100357635A CN101081638B (en) | 2006-06-02 | 2006-06-02 | Unmanned aerial plane launching system and method |
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| Publication Number | Publication Date |
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| CN101081638A CN101081638A (en) | 2007-12-05 |
| CN101081638B true CN101081638B (en) | 2010-11-17 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN2006100357635A Expired - Fee Related CN101081638B (en) | 2006-06-02 | 2006-06-02 | Unmanned aerial plane launching system and method |
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Families Citing this family (12)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN102040005A (en) * | 2009-10-12 | 2011-05-04 | 张新华 | Safe, efficient, energy-saving and novel boosting method and device for takeoff of aircraft carrier-based plane |
| CN102020021B (en) * | 2011-01-04 | 2013-02-06 | 贾正跃 | Reverse pulling and prompt release assisted takeoff method for realizing short-range take-off of aircraft carrier-based plane |
| CN102923312A (en) * | 2012-10-18 | 2013-02-13 | 桂林鑫鹰电子科技有限公司 | Small take-off launch frame for unmanned aerial vehicle |
| CN103910069A (en) * | 2013-01-03 | 2014-07-09 | 滕德选 | Aircraft catapult driven by jet engine |
| CN103803095B (en) * | 2014-03-03 | 2016-05-25 | 重庆翼动科技有限公司 | The Pneumatic catapult of SUAV |
| CN104015933B (en) * | 2014-06-11 | 2016-03-30 | 毕和军 | Collapsible unmanned aerial vehicle ejecting regenerative apparatus |
| WO2017184552A1 (en) * | 2016-04-20 | 2017-10-26 | Engineered Arresting Systems Corporation | Electric unmanned aerial vehicle launcher |
| CN106143941B (en) * | 2016-08-12 | 2018-05-04 | 成都德坤航空设备制造有限公司 | A kind of truck platform for the transmitting of small-sized fixed-wing unmanned plane |
| CN109398737B (en) * | 2018-09-28 | 2021-11-23 | 江苏润翔软件技术有限公司 | Unmanned aerial vehicle who uses new generation information technology casts device |
| CN111348191A (en) * | 2018-12-20 | 2020-06-30 | 中国航空工业集团公司西安飞机设计研究所 | Backward ejection type unmanned aerial vehicle launching method |
| US11628952B1 (en) | 2022-02-10 | 2023-04-18 | Censys Technologies Corporation | Constant torque UAV device, method and system |
| CN114802794B (en) * | 2022-05-24 | 2023-02-10 | 西北工业大学 | Diamond-layout flexible unmanned aerial vehicle hanging tilting system and control method |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1490164A (en) * | 1976-03-17 | 1977-10-26 | Airfix Prod Ltd | Toy |
| US4079901A (en) * | 1976-04-07 | 1978-03-21 | All American Industries, Inc. | Launching apparatus for flying device |
| US5423706A (en) * | 1994-01-28 | 1995-06-13 | Chase; George W. | Toy aircraft glider with rotating and folding wings |
| GB2293146A (en) * | 1994-09-15 | 1996-03-20 | Airscrew Howden Ltd | Launching projectiles |
| US6851647B1 (en) * | 2003-04-03 | 2005-02-08 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Portable catapult launcher for small aircraft |
| CN200960979Y (en) * | 2006-06-02 | 2007-10-17 | 珠海星宇模型实业有限公司 | Transmission system for unmanned machine |
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2006
- 2006-06-02 CN CN2006100357635A patent/CN101081638B/en not_active Expired - Fee Related
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1490164A (en) * | 1976-03-17 | 1977-10-26 | Airfix Prod Ltd | Toy |
| US4079901A (en) * | 1976-04-07 | 1978-03-21 | All American Industries, Inc. | Launching apparatus for flying device |
| US5423706A (en) * | 1994-01-28 | 1995-06-13 | Chase; George W. | Toy aircraft glider with rotating and folding wings |
| GB2293146A (en) * | 1994-09-15 | 1996-03-20 | Airscrew Howden Ltd | Launching projectiles |
| US6851647B1 (en) * | 2003-04-03 | 2005-02-08 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Portable catapult launcher for small aircraft |
| CN200960979Y (en) * | 2006-06-02 | 2007-10-17 | 珠海星宇模型实业有限公司 | Transmission system for unmanned machine |
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| Publication number | Publication date |
|---|---|
| CN101081638A (en) | 2007-12-05 |
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